The basic aeroelastic integral equation is formulated by treating the wing as a tapered cantilever beam mounted normal to its straight elastic axis. By means of an iterative process, a series solution is obtained for the aeroelastic change in angle-of-attack distribution. For sweptback wings, this Neumann solution fails to converge at dynamic pressures that exceed the absolute value of the divergence dynamic pressure, even though the latter is negative and the wing physically stable. This eigenvalue problem is handled by expanding the series about a new point and thus effectively increasing the radius of convergence to agree with the physical case. I t is shown that the new point, expressed by a convergence factor, can be chosen so as to improve the rate of convergence of the series. The aeroelastic effects on the stability derivatives, on the hinge moments, and on the effectiveness of the control surfaces are investigated and shown to be expressible as simple functions of the dynamic pressure. Wind-tunnel data for a full-scale sweptback wing are presented and agree well with results calculated using the present method.